Siemens Energy, Inc.

Siemens Power Generation, Inc.

Bradley T Youngblood

Robert W Dawson

Maz Sutcu

Robert James Bland

Ricardo Ferreira Moraes

James Michael Zborovsky

Sanjay Chopra

An apparatus is provided for coupling a first portion of a gas turbine transition duct to a second portion of a gas turbine transition duct to reduce vibratory deflection. The apparatus may comprise: at least one first support structure attached to the gas turbine transition duct first portion; at least one second support structure attached to the gas turbine transition duct second portion; and at least one coupling mechanism configured to couple the at least one first support structure to the at least one second support structure so as to allow sliding movement between the at least one first support structure and the at least one second support structure when a movement force of the at least one first support structure and the at least one second support structure exceeds a predefined frictional force threshold value.

Gas turbine transition duct coupling apparatus

A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.

Transition support system for combustion transition ducts for turbine engines

Embodiments of a transition () of the present invention comprise a cooling channel () defined in part by an outer wall () and an inner wall (). The cooling channel () also comprises lateral side walls (). Two or more subdomains (AA, BB, A, B, B, C, C, D) of impingement jets () are provided through the outer wall (), and one or more metering outlets () is provided through the inner wall (), all communicating with a respective channel (). The impingement jets of each respective subdomain are designed to supply cooling fluid to one of the one or more metering outlets. Further to the impingement jets () their size, shape, spacing, and arrangement with regard to the metering outlet () are such that a desired cooling of the inner wall () is provided during normal gas turbine operations through advantageous impingement cooling at points along the surface of the inner wall () that defines the cooling channel ().

Impingement jets coupled to cooling channels for transition cooling

A transition () for a gas turbine engine () comprises a transition wall () comprising cooling channels (L,R,L,R) that are adapted to pass a cooling fluid, such as compressed air from a compressor () during operation of the gas turbine engine () so as to cool combusted hot gases passing through the transition (). For each cooling channel (L,R,L,R), respective entry ports (L,L,L,R) and exit ports (L,R,L,R) are arranged so as to obtain a performance improvement based upon pressure differentials between the respective entry and exit ports. In various embodiments, a scoop () is associated with an entry port (L,R) so as to establish a more elevated pressure differential in the respective cooling channel (L,R). An entry port (-) may be positioned offset relative to a lower-positioned exit port (-) so as to so minimize or eliminate intake of heated airflow from a respective nearby exit port (-). Such offset positioning may be based on the airflow paths and cooling requirements at selected high-temperature operating conditions.

Gas turbine engine transitions comprising closed cooled transition cooling channels

A heat shield for a transition of a turbine engine for coupling a transition component of a turbine engine to a turbine vane assembly to direct combustor exhaust gases from the transition into the turbine vane assembly. The heat shield may be capable of reducing the temperature differential across a transition bracket extending from a transition component, thereby reducing the likelihood of premature failure of the bracket or the transition, or both. The heat shield may reduce the temperature differential by insulating the transition bracket and transition bracket rib from cooling gases. The heat shield may be formed from a tubular elongated body having first and second end attachments configured to attach the elongated heat shield body to the transition.

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Oviedo, FL, United States of America

Bradley T Youngblood